PZL-105 Flaming
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| PZL-105 Flaming | |
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 PZL-105 at the Polish Aviation Museum |
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| Type | Utility aircraft |
| Manufacturer | PZL Warszawa-Okęcie |
| Maiden flight | 9 November 1989 |
| Status | Prototype |
| Primary user | Polish civilian aviation |
| Number built | 2 (prototypes) |
PZL-105 Flaming (Flamingo) is a Polish short-takeoff-and-landing (STOL) utility aircraft designed by PZL "Warszawa-Okęcie". It remained a prototype.
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[edit] Design and development
The PZL-105 was designed as a successor to a successful utility aircraft PZL-104 Wilga, more modern and economical and offering increased transport capacity. The design was initially called Wilga 88. It retained high-wing layout of the PZL-104 and side doors opening upwards, but it is a completely new plane. Comparing to the Wilga, it has six-place cab instead of four-place and wings are supported with single struts instead of a cantilever design. The plane was intended for a variety of purposes, like glider towing, parachute training, transport, air ambulance, patrolling and crop dusting (with 500 kg of chemicals). Also a seaplane variant was intended.
The first prototype, powered with 265 kW (360 hp) Russian M-14P radial engine, was flown on 9 November 1989 (markings SP-PRC). An intended designation of a serial variant was PZL-105M. The second prototype, designated PZL-105L, was fitted with a flat engine 298 kW (400 hp) Lycoming IO-720. It was flown on 27 July 1991 (markings SP-PRD). There was also made one prototype for static trials.
Problems with funding at the outbreak of 1980s and 1990s, connected with a change of political system in Poland, and a priority of PZL-130 Orlik trainer program, caused, that the Flaming program was suspended and the production has not started. The factory developed a new variant of PZL-104, the Wilga 2000 with Lycoming I0-540 flat engine instead.
[edit] Survivors
The first prototype and the second prototype airframe (lacking engine) are in a colection of the Polish Aviation Museum in Kraków.
[edit] Specifications (PZL-105L)
[edit] Description
Metal construction braced high-wing monoplane, conventional in layout, duralumin covered. Semi-monocoque fuselage. Rectangular single-spar wings, fitted with Fowler flaps and slotted flaperons. Six seat cabin, in three rows, with large side doors, opening upwards. Conventional fixed landing gear with tail wheel, the main gear is made of composite spring legs. Two-blade or three-blade (PZL-105L) metal propeller. Fuel tanks in wings (270 l).
General characteristics
- Crew: 1 pilot
- Capacity: 5
- Length: 8.67 m (28 ft 5¼ in)
- Wingspan: 12.97 m (42 ft 6½ in)
- Height: 2.87 m (9 ft 5 in)
- Wing area: 16.90 m² (182 ft²)
- Empty weight: 1,150 kg (2,530 lb)
- Loaded weight: 1,850 kg (4,070 lb)
- Useful load: 700 kg (1,540 lb)
- Powerplant: 1× Lycoming IO-720-A1B air-cooled flat engine, 298 kW (400 hp)
- *Fuel - 270 l
Performance
- Maximum speed: 260 km/h (140 knots, 161 mph)
- Cruise speed: 235 km/h (127 knots, 146 mph)
- Stall speed: 102 km/h (55 knots, 63 mph)
- Range: 980 km (529 nm, 609 mi)
- Service ceiling 5,000 m (16,400 ft)
- Rate of climb: 5.6 m/s (1,100 ft/min)
- Wing loading: 109 kg/m² (22.4 lb/ft²)
- Power/mass: 0.161 kW/kg (0.0982 hp/lb)
[edit] External links
[edit] References
- Andrzej Glass: Samoloty '94, Grupa IMAGE, Warsaw 1994, ISBN 83-85461-19-1
[edit] See also
Related development PZL-104 Wilga
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